[go: up one dir, main page]

FR3102203B1 - Sealing device for an aircraft turbine engine blade - Google Patents

Sealing device for an aircraft turbine engine blade Download PDF

Info

Publication number
FR3102203B1
FR3102203B1 FR1911590A FR1911590A FR3102203B1 FR 3102203 B1 FR3102203 B1 FR 3102203B1 FR 1911590 A FR1911590 A FR 1911590A FR 1911590 A FR1911590 A FR 1911590A FR 3102203 B1 FR3102203 B1 FR 3102203B1
Authority
FR
France
Prior art keywords
blades
blade
turbine engine
sealing device
engine blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR1911590A
Other languages
French (fr)
Other versions
FR3102203A1 (en
Inventor
Steven Gérard Joseph Bienvenu
Damien Bruno Lamouche
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1911590A priority Critical patent/FR3102203B1/en
Publication of FR3102203A1 publication Critical patent/FR3102203A1/en
Application granted granted Critical
Publication of FR3102203B1 publication Critical patent/FR3102203B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Abstract

La présente invention concerne un dispositif d’étanchéité (50) pour une aube (3) de turbomachine, en particulier d’aéronef, ledit dispositif (50) comprend :- un corps (52) comportant deux lames latérales allongées (52a, 52b) configurées pour enserrer entre elles ladite aube (3), lesdites lames (52a, 52b) comportant des premières extrémités longitudinales (54a, 54b) reliées ensemble et des secondes extrémités longitudinales (56a, 56b) configurées pour être fixées l’une à l’autre, une première (52a) de ces lames étant configurée pour s’étendre du côté d’un intrados (3c) de l’aube et une seconde (52b) de ces lames étant configurée pour s’étendre du côté d’un extrados (3d) de l’aube,- un joint d’étanchéité (58) de forme allongée qui s’étend le long des lames (52a, 52b) et qui est configuré pour coopérer à étanchéité avec lesdits intrados (3c) et extrados (3d) de l’aube, ce joint (58) étant surmoulé sur les lames (52a, 52b). Figure de l’abrégé : Figure 6The present invention relates to a sealing device (50) for a blade (3) of a turbine engine, in particular an aircraft, said device (50) comprises:- a body (52) comprising two elongated side blades (52a, 52b) configured to grip between them said vane (3), said blades (52a, 52b) comprising first longitudinal ends (54a, 54b) connected together and second longitudinal ends (56a, 56b) configured to be fixed to one another, a first (52a) of these blades being configured to extend on the side of a lower surface (3c) of the blade and a second (52b) of these blades being configured to extend on the side of an upper surface (3d) of the blade, - a seal (58) of elongated shape which extends along the blades (52a, 52b) and which is configured to cooperate in sealing with said intrados (3c) and extrados ( 3d) of the blade, this gasket (58) being molded onto the blades (52a, 52b). Abstract Figure: Figure 6

FR1911590A 2019-10-17 2019-10-17 Sealing device for an aircraft turbine engine blade Active FR3102203B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1911590A FR3102203B1 (en) 2019-10-17 2019-10-17 Sealing device for an aircraft turbine engine blade

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1911590A FR3102203B1 (en) 2019-10-17 2019-10-17 Sealing device for an aircraft turbine engine blade
FR1911590 2019-10-17

Publications (2)

Publication Number Publication Date
FR3102203A1 FR3102203A1 (en) 2021-04-23
FR3102203B1 true FR3102203B1 (en) 2022-05-27

Family

ID=68807181

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1911590A Active FR3102203B1 (en) 2019-10-17 2019-10-17 Sealing device for an aircraft turbine engine blade

Country Status (1)

Country Link
FR (1) FR3102203B1 (en)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2490858B (en) * 2011-03-22 2014-01-01 Rolls Royce Plc A bladed rotor
US9017033B2 (en) * 2012-06-07 2015-04-28 United Technologies Corporation Fan blade platform

Also Published As

Publication number Publication date
FR3102203A1 (en) 2021-04-23

Similar Documents

Publication Publication Date Title
FR3099221B1 (en) Aircraft seal
EP1793083A3 (en) Cooled turbine blade with enhanced lifespan
FR2429323A1 (en) STRUCTURE FOR SEALING A ROTARY VALVE IN AN INTERNAL COMBUSTION ENGINE
MA42097B1 (en) Serrated leakage edge panel for a wind turbine blade
EP1757796A2 (en) Compressor having a plurality of segments reconstructing an annular volume and thus separating the flow in a turbomachine
FR3081185B1 (en) TURBOMACHINE STATOR ELEMENT
FR3095830B1 (en) TURBOMACHINE MODULE EQUIPPED WITH A SEALING FLAP HOLDING DEVICE
FR3102203B1 (en) Sealing device for an aircraft turbine engine blade
FR3082233B1 (en) TURBINE SET
FR3070715B1 (en) AIRCRAFT TURBOMACHINE INTER SECTOR SEALING TAPE
FR3059907B1 (en) DEVICE FOR ANCHORING WITHOUT SUTURING A HEART PUMP
FR3109794B1 (en) PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE
FR3107079B1 (en) AIRCRAFT TURBOMACHINE BLADE
MA33359B1 (en) AUBES PRESSURE WHEEL
FR3107922B1 (en) TURBOMACHINE VANE FOILER
FR3137120B1 (en) Turbomachine blade assembly comprising means for limiting vibrations between platforms
FR3095193B1 (en) Method of using a turbojet nacelle air inlet comprising an air inlet lip comprising a movable portion to promote a thrust reversal phase
FR3089561B1 (en) IMPROVED AIR TIGHTNESS DEVICE INTENDED TO BE INTERPOSED BETWEEN A DOUBLE-FLOW AIRCRAFT TURBOMACHINE CASING ELEMENT, AND A NACELLE ELEMENT
FR3070714B1 (en) TURBOMACHINE VANE WITH IMPROVED COOLING HOLES
FR3084398B1 (en) TURBINE VANE
FR3074217B1 (en) DAWN FOR AN AIRCRAFT TURBOMACHINE
FR3079211B1 (en) AIRCRAFT PROPULSION ASSEMBLY COMPRISING TWO ADJACENT ENGINES, OF WHICH THE OUTLET PIPES PRESENT A RIGHT PORTION NEAR A MEDIAN PLANE OF THE PROPULSION ASSEMBLY
FR3118093B1 (en) Turbine blade, in particular for a counter-rotating turbine
FR3103209B1 (en) Labyrinth seal comprising a sliding abradable element
FR3103855B1 (en) Improved blade leading edge structure.

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210423

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6